Aeroplane frame



April 5, 1932., R. G. HuGGlNs 1,852,208

EROPLANE FRAME Filed 11pm 11, 19:51 3 sheets-she'et 1 R. G4 HUGGINS AEROPLANE FRAME April- 5, 1932.

Filed April 11, 1931 3 Sheets-Sheet 2 Patented Apr. 5, 1932 UNITED STATESK retazos ROBE-BT GUY HUGGINS, OF TULSA, OKLAHOMA ALEROPLANE FRAME,

Application led April 11,

This invention relates generally to aeroplane frame construction and particularly to Va new andnovel aeroplane frame and method of composing and constructing the same,` and v adapted to act as a foundation or skeleton for vthe aeroplane and to carry the units thereof in perfect and rigid alignment.

It isan object gof this invention to pro- Vvvide an aeroplane construction of the type described which will be constructed through- Vout of metal, the wing assembly being detachable from lthe fuselage assembly, so 'formed and constructed as to considerably reduce the cost of production of aeroplane l5 frame constructions, by simplifying not only the structure itself but the operations required in making and assembling the same.

It is also an object of this invention to provide pressed metal channel sections of the above the side members 5 as seen in Figure 4. 7

type described in an aeroplane frame construction.

These and other objects of the invention,

its nature, its composition and arrangement and combination of parts will be readily und derstood by any one acquainted with the art to which this invention relates upon consulting the following descriptions of the drawings, in which:

Figure 1 is a top plan view of my improved aeroplane frame partly broken away.

Figure 2 is a vertical transverse section looking in the direction of the arrows approximately on the line 2-2 of Figure 1.

Figure 3 is another transverse vertical cross sectional viewlooking in the direction of the arrowsV approximately on the line 3 3 of Figure 1.

Figure 4 is a side elevational view of Figure 1.

-0 Figure 5 is a front elevational view taken from the left of Figure 1. Figure 6 is an elevational view of one of the channeled members showing the manner of bracing the same.

Figure 7 is a longitudinal vertical sectional view taken through the fore part of the fuse lage frame looking in the direction of the arrows approximately on the line 7 7 of Figure 1.

Figure 8 is a horizontal sectional view thefree end of the cross brace rods 17. The

1931. serial no. 529,489.

taken approximately on the line 8-8 of Figure 4 looking in the direction of the arrows. Figure 9 is a vertical longitudinal sectional Viewv through Figure 6.

Figure 10` is a top plan view of Figure 6. F y Referring in detail to the drawings, the

' numerals 5 refer generally to pressed metal `side members or channel cross sections which make up the fuselage frame and are Vspaced and braced by suitable cross `members 6, 7 f and 8, the cross members being secured between the lianges of the channel shown particularly well in Figures 2 and 3, as well as in Figure 7. The cross member 7 is somewhat rearward of an intermediate point of the i5 fuselage, and from this point the side members may converge as at 9 and 10, and they meet to form a point at 11 where they are attached to a vertical tail post 12 wliichrises At the fore part of the fuselage, the side members 5 converge inwardly as at 13 and 14 justbeyond or at their po-int of attachment to the front cross member 8. The forward ends 15 of these portions are spaced as shown at 15.v A pair of parallel brace members 16 leads from the forward extremity of the portions 13 and 14 of the side A:members 5 and meet the cross member 8 and are-rigidly attached thereto, preferably by welding 'or other suitable attaching means. Itv should be said that the cross members 6 and 7 are also preferably welded to the side members 5, as is the tail post 12. lt will be noticed in the drawings that the channel members or side members 5 are suitably braced with adjust- Aable cross rods 17 arranged in any suitable manner, and comprising the general type of adjustable brace rods illustrated in detail in f Figures v6` and 9 wherein the iianges of the channel members are shown provided with 'countersunk angular bores or depressions 18 carrying an adjusting screwY 19 adapted to draw upon a screw-threaded portion 20' on .Q5

flange ofthe channel member. 'Throughout ,QQ

the drawings, the numeral 22 refers to lower flanges of the fuselage side members stamped or otherwise formed holes in the cross members designed to reduce the weight Y thereof.

Referringto the wing structure, it Awill be observed that it is composed of parallelly or otherwise spaced channel members 23 attached to the underside of the fuselage frame, in a detachable manner as seen in detail in Figures 2. and 3 as well as 7. Bolts or the like attaching means of a detachable character indicated atQArare passed through the and through the upper flanges of the side members 23 of the wing assembly.

Similarly to the fuselage frame or assembly, the wing assembly is cross braced by i. similar brace rods 17 in order to lend rigidity and to equalizeV the stresses which itY is vto undergo. There 1s a difference, however, in the manner ofplacement of the"wing assem- 4bly brace Yrods as seen in Figures Zand 'The manner of placlng the brace rods in Figures 6 and 9 as well as l0 refers particularly to the fuselage frame or assembly. Referringrto Figures 2 and 3 which are pertinent to the wing assembly, it will be seen that the brace rods 17a are at their end portions passed I through the cross brace members 2A: ywhich space the side members 23 of the wing assembly. Y

The essence of this invention is comprised .Y in the employmentof channel section pressed metal members in the frame of an aeroplane,

looking to superior rigidity, greater simplicity and a considerable reduction in `production costs through reduction of 'amount of material used and operations involved, as

f compared to presently known structures of this general type.

Therefore, it will be denitely understood that I do not desire to limit the application of this invention to the particular modification set out herein to illustrate the principles lthereof,land any change lor changes may be vmade inmaterial and structure consistent with the scope of the invention.

What is claimed is l. Anaeroplane frame `construction of the i type described employing a fuselage assembly composed of transversely spacedv side vmembers of pressed'metal channel sections,

and-a ydetachable wing assembly similarly gmade, and longitudinally adjustable brace rods between each pair of said members, as

well as rigid cross members. Y. Y

2. An aeroplane frame construction ofthe members of pressed metal channel sections, and a detachable wing assembly similarly lmade, and longitudinally adjustable brace rods between each pair of said members and Ythe members vof the wing assembly, rigid cross members spacing the members ofthe fuselage and wing assemblies, and an engine j fuselage.

support comprising a forwardv extension of the fuselage Vassembly side members and parallel longitudinal brace members connected between the ends of said last mentioned side members and a forward one of said rigid cross members, said wing assembly being secured to the side members rearwardly of said engine support.

An aeroplane frame construction of the type described employing a fuselage assemly composed of a pair of transversely spaced side members of pressed metal channel sections and a detachable wing assembly similarly made, and adjustable brace rods between spaced side members inthe form of pressed sov metal channels, and a detachable wing assembly similarly made, and adjustableubrace rods between each pair of side and wing members, as well as rigid cross members rfor spacing the side members, said wing assembly Vbeing secured under said spaced side members of the fuselage, and the rear ends of theside members of the fuselager assembly being converged, and a tailpost, attached at their point of meeting'. y V

In testimony whereof I aiiX my signature.

ROBERT GUY HUGGINS.

type described employing a fuselage assem- I o bly composed of transversely spaced side IRO 

